Aircraft seed broadcasting systems, apparatus and methods

ABSTRACT

An aerial seeding system that may be installed in an aircraft in a modular form with minimal modification to the existing aircraft configuration, and, in particular, without any structural modifications that would adversely impact the integrity of the aircraft structure or its overall air worthiness. Exemplary embodiments include an active and controllable seed distribution mechanism to ensure continuously controllable and even distribution of seeds. Basic system components include a modular seed hopper, a seed broadcasting head and a hydraulic system driven by a pump connected to an aircraft accessory drive.

RELATED APPLICATION DATA

This application claims the benefit of priority of U.S. ProvisionalPatent Application Ser. No. 62/199,688, filed on Jul. 31, 2015, andtitled “Aircraft Seed Broadcasting Apparatus,” which is incorporated byreference herein in its entirety.

FIELD OF THE INVENTION

The present disclosure relates to aircraft seed broadcasting, and, moreparticularly, to modularized systems, and related apparatus and methodsto provide aircraft mounted seed broadcasting without structuralmodifications to the aircraft.

BACKGROUND

Potential advantages associated with aerial seeding or sowing arewell-known in the agricultural industry. However, in spite of thepotential, systems for aerial seeding are not well designed to exploitthose advantages. Existing systems fall into generally two categories:systems based on crop dusting technology utilizing modifications tonozzle/sprayer systems intended primarily for liquids/pesticideapplication, and passive systems that utilize buckets, chutes or similarstructures and which rely primarily on the turbulence surrounding theaircraft in motion to distribute the seeds.

One challenge in creating an effective aerial seeding system is that inmost countries modifications to licensed aircraft, such as airplanes andhelicopters, must be approved by a governmental agency to ensure safetyand airworthiness. In the United States, the agency is the FederalAviation Administration (FAA). Under FAA regulations, not justmodification, but also addition of equipment must meet stringentapproval requirements. Thus, while the patent literature containsnumerous different design proposals for seeding systems, few of theseare practical or even useable due to the fact that they require eitheran entirely new aircraft or extensive changes, additions ormodifications to be mounted and flown in an existing aircraft.

SUMMARY OF THE DISCLOSURE

In one implementation, the present disclosure is directed to an aircraftseed broadcasting system that includes a seed hopper configured anddimensioned to be insertable through a door frame of an aircraft andmountable to pre-existing aircraft mounting points; a broadcasting headconfigured and dimensioned to be mounted to an underside of the aircraftfuselage below the seed hopper to broadcast seeds received from hopper;and a power supply system configured to drive the broadcasting head.

In another implementation, the present disclosure is directed to anaircraft seed broadcasting system that includes a seed hopper comprisingplural separable members each configured and dimensioned to beinsertable individually through a passenger door frame of an aircraft,assembled into the seed hopper within the aircraft and mounted toexisting passenger seat and seatbelt attachment points; a broadcastinghead comprising a body defining a seed plenum leading to a motor drivenrotating distribution disk, the body configured and dimensioned to bemounted along a centerline on an underside of the aircraft fuselagebelow the assembled and mounted seed hopper to receive seeds from thehopper; and power supply components configured to provide aircraftsupplied power to the motor driven rotating distribution disk.

In yet another implementation, the present disclosure is directed to amethod of installing a seed broadcasting system in an aircraft. Themethod includes removing an aircraft passenger seat from a passengerspace; inserting a seed hopper through an aircraft passenger door intothe passenger space; forming at least one hole through a non-structuralfuselage skin portion on the bottom of the aircraft in the passengerspace; mounting the seed hopper to pre-existing mounting points in thepassenger space with a feed chute extending through the at least onehole in the fuselage skin; mounting a seed broadcasting head including amotor driven rotating distribution disk on an underside of the aircraftfuselage in a position to communicate with the feed chute through the atleast one hole to receive seeds therefrom; and connecting a broadcastinghydraulic system to a hydraulic pump driven by an accessory drive topower the motor driven rotating head.

DESCRIPTION OF THE DRAWINGS

For the purpose of illustrating the invention, the drawings show aspectsof one or more embodiments disclosed herein. However, it should beunderstood that the inventions embodied in this disclosure are notlimited to the precise arrangements and instrumentalities shown in thedrawings, wherein:

FIG. 1 is a partial starboard side view of an aircraft with an exemplaryembodiment of an aerial seed broadcasting system installed therein.

FIG. 2 is a partial port side view of the aircraft shown in FIG. 1 withthe embodiment of the disclosed system.

FIG. 3 is a detailed view of the rear seat area where portions of theexemplary broadcasting system are installed.

FIG. 4 is a view of a hopper bottom installed in an aircraft inaccordance with an exemplary embodiment disclosed herein.

FIG. 5 is a view of a partially assembled hopper, with hopper wallsmounted on the hopper bottom shown in FIG. 4.

FIG. 6 is a detailed view of a seed broadcasting head according to anexemplary embodiment of the present disclosure, mounted on the undersideof the aircraft fuselage.

FIG. 7 is a close view of the broadcasting head shown in FIG. 6 with aseed delivery duct removed for illustration purposes.

FIG. 8 is a detailed plan view of internal components of thebroadcasting head shown in FIG. 6.

DETAILED DESCRIPTION

Embodiments disclosed herein provide a system for aerial broadcasting ofseeds or other similar materials in modular form to facilitateinstallation and removal from the aircraft. Also disclosed are methodsfor installing such a modular system without altering airworthiness.Modules may generally comprise a seed hopper, broadcasting head andhydraulic supply components. In one embodiment disclosed herein, asshown in FIGS. 1 and 2, an aircraft seed broadcasting system includes aseed hopper 10 mountable in a passenger space or rear seat area of theaircraft, and a broadcasting head 12 mounted to the underside of theaircraft fuselage to broadcast seeds received from hopper 10. A seedinput port 14 is provided in an upper portion of the hopper wall, andsight gage 16 allows an operator to visually determine the fill level ofthe hopper. Vents 18, 20 are provided at the top of hopper 10.

Components of disclosed embodiments may be readily fabricated fromaviation quality materials and incorporated into the aircraft with aminimum of alteration to the aircraft. In one illustrative example, anembodiment of the disclosed system is installed in a four-place R-44series helicopter by the Robinson Helicopter Company as shown in thepresent figures. As will be appreciated by those skilled in the art, thedisclosed system may be readily adapted to other aircraft types withoutsignificant changes. While persons of ordinary skill may adaptembodiments disclosed herein to virtually any aircraft, aircraft mostsuited for use with embodiments of the invention include fixed wing orhelicopter aircraft with a passenger space/seat positioned behind thepilot position, enterable by at least one passenger door. To facilitateinstallation and minimize aircraft alterations, attachment points forsystem components may solely comprise preexisting aircraft mountingpoints, such as seat support structure and seatbelt attachments. In theillustrated example, hopper 10 is mounted in the rear passengercompartment with attachment points encompassing all six of the seat belthard points to secure the unit.

As described in more detail below and shown in FIG. 2, broadcasting head12 is powered by a hydraulic motor which receives hydraulic fluidpressure generated by an existing aircraft system, such as the airconditioning system. In the illustrated Robinson R-44 embodiment, systempower is provided by a factory-approved air conditioning drive mountedto the left-hand, rear drive pad of the O-540 engine. A separatehydraulic tank 22 is provided for the broadcasting head hydraulicsystem. Tank 22 has a tank vent 24 and hydraulic supply and return lines28, 25. The hydraulic lines are routed to broadcasting head 12 viaconduit 26.

As illustrated in FIG. 2, hydraulic tank 22 may be attached to the leftside of the R-44 helicopter using two 0.75×0.040 stainless steel bandclamps fastened to 0.050 plate of 2024 T3 aluminum with fourMS27039-1-20 screws, four AN970-3 washers and four MS21042L3 nuts. The0.050 plate is attached to the helicopter using five preexistingMS21069L08 nut plates and five MS27039-0808 screws along the forwardfacing and top edge of the plate. Two additional MS27039-1-14 screws,two MS21042L3 nuts and two MS21919WDG16 clamps attach the middle and aftledge of the plate to the C046-19 Robinson lower-left frame assembly.

To install hopper 10, the rear seat of the aircraft is removed andhopper mounting stringer 30 is bolted to the existing seat supportstructure as shown in FIG. 3. In one exemplary embodiment asillustrated, stringer 30 may be constructed out of 0.032 2024 T3aluminum and fitted with 12 MS21075-08L nut plates where 12 MS27039-0808screws attach the stringer to the vertical forward face of the seatbottom using the pre-existing holes that the seat cushions utilize whenthe seat bottoms are installed. Stringer 30, once installed, providestwenty MS21075-08L nut plates to which the hopper bottom can be attachedto the airframe.

Hopper 10 may be constructed from six sub-panels. Hopper bottom 32,including generally pyramid-shaped feed chutes 34A, 34B, is bolted tostringer 30 through bolt holes 36 as shown in FIG. 4. In an exemplaryembodiment, twenty bolt holes 36 are provided to accommodate twentyMS27039-0808 screws that pass down through the hopper bottom 32 andattach to stringer 30. Mounting brackets 38 provide for connection tomiddle rear seat seatbelt attachment points.

Hopper bottom 32 may be constructed out of 0.040 2024-T3 aluminum andriveted together with MS20470AD4-4 rivets. The attachment points and thefour angles that encompass the perimeter of the panel are constructedfrom 6061T6 aluminum. There are four one inch angles which havetwenty-two MS21075-08L nut plates riveted in place on a five inchspacing pattern to provide attachment points for the four vertical sidepanels of the hopper to attach to. Three panels, rear wall 40, forwardwall 42 and starboard wall 44, are shown in FIG. 5. The port wall isremoved to permit viewing of the interior of the hopper. The side panelsmaking up the four hopper vertical walls may be constructed from 0.0322024-T3 aluminum. The forward and aft walls 42, 40, may have three oneinch angles constructed from 6061T6 aluminum and riveted to these panelsusing MS20470AD4-4 rivets with eighteen MS21075-08L nut plates rivetedin place on a five inch spacing pattern. The left and right walls may beconstructed out of 0.032 2024-T3 aluminum and have one 6061T6 aluminumone inch angle attached to the top edge of these panels which holds 5MS21075-08L nut plates on a five inch spacing pattern. The hopper top(not shown in the figures) may be constructed from 0.020 2024-T3aluminum. Each hopper sidewall is provided with an interior stiffeningmember 48, 50, 54. All six hopper panels are attached together utilizingthe MS21075-08L nut plates and MS27039-0808 screws. All the panels areremovable in order to fit hopper 10 into the aircraft one panel at atime so that the hopper may be assembled within the passenger space.

Attachment brackets 55A, 55B are each attached to hopper 10 and to theaircraft rear seatbelt top attachment points. As best seen in FIG. 5(also FIGS. 1 and 2), bracket 55A is located on the left-hand side ofthe aircraft and the head of the NAS6604-18 bolt that the OEM uses toattach to the shoulder harness guide assembly of the seatbelt to theairframe can be seen.

In order to provide communication between hopper 10 within the aircraftcabin, and broadcasting head 12 located under the fuselage, two holesare cut in a non-structural portion of the fuselage belly skin undereach passenger rear seat to receive the outlets of each of feed chutes34A, 34B (FIG. 4). The shape of the feed chutes and position of thebroadcasting head directly under the feed chutes allows for gravity feedof materials to be broadcast from hopper 10 directly into broadcastinghead 12. In one exemplary embodiment, the two holes may be four inchesin diameter and strengthened with an aluminum 2024-T3 0.032 ring doublerand fitted with six nut plates and riveted in place in accordance withFAA Reg. 43.13. As illustrated by FIGS. 6-8, seeds or other material tobe broadcast is delivered to rotating distribution disk 56 of broadcasthead 12 from feed chutes 34A, 34B via delivery ducts 62A, 62B and thenthrough head body 60. The delivery ducts may have a flat, angled bottomto direct materials to the head body. In one embodiment, the deliveryduct bottom angle may be at about 12°.

As shown in FIG. 7, in which delivery duct 62B is removed to facilitateview of other parts, connector duct 64B connects the outlet of feedchute 34B with delivery duct 62B. Gasket 66B prevents leakage ofmaterials passing therethrough. Materials delivery into head body 60 isthrough door 68B, controlled by remotely controlled slide gate 70B. Itshould be noted that the structure shown in FIG. 7 corresponds to thestarboard side of broadcasting head 12 and that the same structure ismirrored on the port side.

Materials passing through doors 68A, 68B are received in head body 60and delivered to distribution disk 56 through plenum 72 as shown in FIG.8. Doors 68A, 68B are driven by actuator servo 74, which connect to eachdoor through actuator arm 76. Rotation of servo 74 delivers forward andaft linear motion, guided by linear slide bearings 78A,B, for each ofdoors 68A, 68B, respectively. A switch for turning linear actuator servo74 on and off may be conveniently located in the cockpit within thepilot's easy reach.

In one exemplary embodiment, the components of broadcasting head 12 maybe constructed out of 6061 aluminum and fastened together with grade 5hardware. Hydraulic motor 58 that drives distribution disc 56 (FIG. 6)may be selected by persons of ordinary skill for compatibility with ahydraulic system including a pump driven off of the aircraft accessorydrive pad. In the example of the Robinson R-44 helicopter as shown inthe figures, a Parker gear pump, part number MGG20016 BB1B3 (not shown),was used. This is the same motor/pump that drives the distribution pumpoff of the OEM air conditioning drive.

Provision of electrical controls for the system disclosed may create asfew as two electrical impacts to the aircraft. The first electricalimpact is a solenoid-type switch controlling the flow of the hydraulicfluid from pump to pump and pump to tank. The second electrical impactis actuator 74 that opens and closes the gravity-fed doors 68A, 68B. Inthe R-44 exemplary embodiment shown, the solenoid switch may be a 12volt solenoid-type switch with a 5 amp circuit breaker, and the actuatormay be a 12 volt linear actuator with a 10 amp circuit breaker.

With a system thus designed, it is possible to maintain weight andbalance within the standard limits aircraft CG and gross weightparameters, both with the system fully loaded and completely empty. Inthe exemplary embodiment of the R-44 helicopter shown in the figures,the entire system installed weighs approximately 91.0 pounds.

The foregoing has been a detailed description of illustrativeembodiments of the invention. It is noted that in the presentspecification and claims appended hereto, conjunctive language such asis used in the phrases “at least one of X, Y and Z” and “one or more ofX, Y, and Z,” unless specifically stated or indicated otherwise, shallbe taken to mean that each item in the conjunctive list can be presentin any number exclusive of every other item in the list or in any numberin combination with any or all other item(s) in the conjunctive list,each of which may also be present in any number. Applying this generalrule, the conjunctive phrases in the foregoing examples in which theconjunctive list consists of X, Y, and Z shall each encompass: one ormore of X; one or more of Y; one or more of Z; one or more of X and oneor more of Y; one or more of Y and one or more of Z; one or more of Xand one or more of Z; and one or more of X, one or more of Y and one ormore of Z.

Various modifications and additions can be made without departing fromthe spirit and scope of this invention. Features of each of the variousembodiments described above may be combined with features of otherdescribed embodiments as appropriate in order to provide a multiplicityof feature combinations in associated new embodiments. Furthermore,while the foregoing describes a number of separate embodiments, what hasbeen described herein is merely illustrative of the application of theprinciples of the present invention. Additionally, although particularmethods herein may be illustrated and/or described as being performed ina specific order, the ordering is highly variable within ordinary skillto achieve aspects of the present disclosure. Accordingly, thisdescription is meant to be taken only by way of example, and not tootherwise limit the scope of this invention.

Exemplary embodiments have been disclosed above and illustrated in theaccompanying drawings. It will be understood by those skilled in the artthat various changes, omissions and additions may be made to that whichis specifically disclosed herein without departing from the spirit andscope of this disclosure.

What is claimed is:
 1. An aircraft seed broadcasting system, comprising:a seed hopper configured and dimensioned to be insertable through a doorframe of an aircraft and mountable to pre-existing aircraft mountingpoints; a broadcasting head configured and dimensioned to be mounted toan underside of the aircraft fuselage below the seed hopper to broadcastseeds received from the seed hopper; and a power supply systemconfigured to drive the broadcasting head; wherein the door frame is apassenger door frame and said pre-existing aircraft mounting pointscomprise a passenger seat support structure and corresponding seatbeltattachment points.
 2. The aircraft seed broadcasting system of claim 1,wherein said power supply system comprises a broadcasting hydraulicsystem configured to be powered by an aircraft accessory drive and thebroadcasting head includes a rotating distribution disk driven by ahydraulic motor.
 3. The aircraft seed broadcasting system of claim 1,wherein said seed hopper comprises plural separable members eachconfigured and dimensioned to be insertable individually through thedoor frame of the aircraft and assemblable into said seed hopper withinthe aircraft.
 4. The aircraft seed broadcasting system of claim 3,wherein one said separable member comprises a hopper bottom defining twospaced-apart feed chutes.
 5. An aircraft seed broadcasting system,comprising: seed hopper configured and dimensioned to be insertablethrough a door frame of an aircraft and mountable to pre-existingaircraft mounting points; a broadcasting head configured and dimensionedto be mounted to an underside of the aircraft fuselage below the seedhopper to broadcast seeds received from the seed hopper; and a powersupply system configure to drive the broadcasting head; wherein saidpower supply system comprises broadcasting hydraulic system configuredto be powered by an aircraft accessory drive and the broadcasting headincludes a rotating distribution disk driven by a hydraulic motor; andwherein the broadcasting hydraulic system includes a hydraulic tankconfigured to be attached to preexisting mounting points on theaircraft.
 6. An aircraft seed broadcasting system, comprising: a seedhopper configured and dimensioned to be insertable through a door frameof an aircraft, and mountable to pre-existing aircraft, mounting points;a broadcasting head configured and dimensioned to be mounted to anunderside of the aircraft fuselage below the seed hopper to broadcastseeds received from the seed hopper; and a power supply systemconfigured to drive the broadcasting head; wherein the broadcasting headcomprises: a motor driven, rotating distribution disk configured todistribute seeds; a body configured to be mounted longitudinally alongthe aircraft centerline and defining a seed plenum communicating with atop of the rotating distribution disk; seed delivery ducts extendingtransversely on opposite sides of the body positioned to convey seedsfrom the hopper to the body; and remotely actuatable seed flow controldoors between each seed delivery duct and the body.
 7. The aircraft seedbroadcasting system of claim 6, wherein said remotely actuated seed flowcontrol doors comprise sliding gates.
 8. The aircraft seed broadcastingsystem of claim 6, wherein the seed hopper comprises a hopper bottomwith two transversely spaced feed chutes, the seed hopper configured anddimensioned to position each said feed chutes above one said seeddelivery duct when installed in the aircraft.
 9. The aircraft seedbroadcasting system of claim 8, wherein the transversely spaced feedchutes are configured to extend through a fuselage skin portion and saidfeed chutes further comprise connectors configured to connect anddeliver seeds from said chutes to said delivery ducts.
 10. The aircraftseed broadcasting system of claim 6, further comprising a broadcastingelectrical system consisting essentially of a switch controlling thedistribution disk motor, and an actuator and switch for controlling theseed flow control doors.
 11. An aircraft seed broadcasting system,comprising: a seed hopper comprising plural separable members eachconfigured and dimensioned to be insertable individually through apassenger door frame of an aircraft, assembled into said seed hopperwithin the aircraft and mounted to existing passenger seat and seatbeltattachment points; a broadcasting head comprising a body defining a seedplenum leading to a motor driven rotating distribution disk, said bodyconfigured and dimensioned to be mounted along a centerline on anunderside of the aircraft fuselage below the assembled and mounted seedhopper to receive seeds from said hopper; and power supply componentsconfigured to provide aircraft supplied power to the motor drivenrotating distribution disk.
 12. The aircraft seed broadcasting system ofclaim 11, further comprising: seed ducts extending transversely onopposite sides of the body, the seed ducts configured to communicatewith a feed chute formed in a bottom of the seed hopper through holes ina non-structural, skin portion of the fuselage; and remotely actuatablegate disposed between each seed duct and the body for controlling flowof seed to the rotating distribution disk.
 13. The aircraft seedbroadcasting system of claim 11, further comprising a hydraulic motordriving the rotating distribution disk, wherein said power supplycomponents comprise broadcasting hydraulic system components configuredto be driven off of an aircraft accessory drive.
 14. The aircraft seedbroadcasting system of claim 13, comprising in combination the aircraftwith the broadcasting hydraulic system including a hydraulic pump drivenby the aircraft accessory drive to provide pressurized hydraulic fluid.15. The aircraft seed broadcasting system of claim 14, wherein saidaircraft is a helicopter.
 16. The aircraft seed broadcasting system ofclaim 14, wherein said hydraulic pump is a gear pump.
 17. A method ofinstalling a seed broadcasting system in an aircraft, comprising:removing an aircraft passenger seat from a passenger space; inserting aseed hopper through an aircraft passenger door into the passenger space;forming at least one hole through a non-structural fuselage skin portionon the bottom of the aircraft in the passenger space; mounting the seedhopper to pre-existing mounting points in the passenger space with afeed chute extending through said at least one hole in the fuselageskin; mounting a seed broadcasting head including a motor drivenrotating distribution disk on an underside of the aircraft fuselage in aposition to communicate with said feed chute through said at least onehole to receive seeds therefrom; and connecting a hydraulic pump to anaircraft accessory drive to power the motor driven rotating head; andwherein said inserting a seed hopper comprises inserting plural,separate seed hopper members through the passenger door and assemblingsaid members to form a seed hopper within the aircraft.
 18. The methodof claim 17, wherein: said seed hopper includes two transversely spacedfeed chutes; said forming at least one hole comprises forming two holestransversely and evenly spaced on opposite sides of the aircraftcenterline corresponding to the spacing of the two feed chutes; and saidmounting the seed hopper further comprises positioning each said feedchute to communicate with the broadcasting head through one said hole.